Foreign object damage elimination system

Patent metadata

Field	Value
Publication number	US-10384807-B2
Application number	US-201515327565-A
Country	US
Kind code	B2
Filing date	Jul 20, 2015
Priority date	Jul 22, 2014
Publication date	Aug 20, 2019
Grant date	Aug 20, 2019

Abstract

An assembly configured to prevent damage to an object during manufacture thereof is provided including a first housing having a substantially hollow interior. An exposed first planar surface of the first housing includes an inlet port and a plurality of small openings formed about the periphery. The inlet port, the hollow interior, and the plurality of small openings form a fluid flow path through the assembly. A second housing similar in size and shape to the first housing, has an exposed second planar surface. An intermediate layer is arranged between the first housing and the second housing. A cross-section of the intermediate layer is configured to change shape in response to a compression force applied thereto by the first housing and the second housing to form a seal separating an exterior portion of the object exposed to the plurality of small openings from an interior surface of the object.

First claim

What is claimed is:

1. A method of cleaning a rotor blade spar, the method comprising: inserting an assembly within a hollow interior of the spar, the assembly having a first housing, a second housing, and an intermediate housing disposed between the first and second housings; forming a seal using the intermediate housing so as to separate an open interior surface of the spar from a closed interior surface of the spar; and generating a flow of fluid into a cavity of the first housing and out of holes in the first housing such that the fluid flows from the assembly toward the open interior surface of the spar without passing into the closed interior surface of the spar.

2. The method according to claim 1 , wherein the assembly is inserted into the hollow interior of the spar such that the assembly is positioned between the closed interior surface at an outboard end of the spar and a critical surface of the spar.

3. The method according to claim 1 , wherein the forming the seal includes compressing the intermediate housing between the first housing and the second housing.

4. The method according to claim 3 , wherein the intermediate housing is compressed by tightening a nut attached to a compression fastener extending through the first housing, the intermediate housing, and the second housing.

5. The method according to claim 1 , wherein the flow of fluid into the cavity is generated by a pump operably coupled to a fluid supply, the fluid supply being one or air or coolant.

Assignees

• Sikorsky Aircraft Corp

Inventors

• Caywood David W
• Ameti Pellumb
• Tabone Michael
• Northrop Kneil

Classifications

• B64F5/40 Primary

  Maintaining or repairing aircraft · CPC title

• B64C2027/4733

  Rotor blades substantially made from particular materials · CPC title

• B64F5/30

  Cleaning aircraft · CPC title

• B24C3/00

  Abrasive blasting machines or devices; Plants · CPC title

• B64C27/473 Primary

  Constructional features · CPC title